Automatic locking hook device for aircraft arresting cable

Abstract

The utility model discloses an automatic locking hook device of an aircraft arresting cable in the technical field of aircraft arresting cables, which comprises an arresting cable, the arresting cable is provided with a locking hook unit, the locking hook unit comprises an elastic locking structure and a connecting structure, the connecting structure is used for connecting the elastic locking structure with the arresting cable, and the locking hook unit is connected with the arresting cable. The elastic locking structure is used for locking the aircraft tail hook and the arresting cable under the action of the force of the aircraft tail hook; by arranging the lock hook unit, the unhooking rate of the tail hook and the arresting cable of the aircraft can be reduced, and then the problems that the risk of landing failure is increased, and the flight safety and the operation efficiency are threatened due to unhooking of the tail hook and the arresting cable are solved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft arresting cable technology, and in particular to an automatic locking hook device for aircraft arresting cables. Background Technology

[0002] Aircraft arresting cables play a crucial role in military airfields and aircraft carriers. They can quickly and effectively slow down and stop an aircraft during landing, ensuring that the aircraft can safely and accurately stop in the designated area. Especially in emergency landings or situations requiring rapid braking, they are key equipment for ensuring the safety of pilots and aircraft.

[0003] During aircraft landing, there may be situations where the tailhook bounces off the ground or the arresting cable, which can easily lead to problems such as poor contact angle between the arresting cable and the tailhook, resulting in detachment. Traditional arresting cables are prone to detachment due to the huge impact force and complex attitude of the aircraft during high-speed landing, increasing the risk of landing failure and threatening flight safety. Utility Model Content

[0004] To overcome the shortcomings of the existing technology, the technical problem to be solved by this utility model is: how to reduce the risk of the tail hook detaching from the arresting cable.

[0005] The technical solution adopted by this utility model to solve its technical problem is:

[0006] An automatic locking device for aircraft arresting cables includes an arresting cable with a locking hook unit. The locking hook unit includes an elastic locking structure and a connecting structure. The connecting structure connects the elastic locking structure and the arresting cable. The elastic locking structure locks the aircraft tailhook and the arresting cable when subjected to the force of the aircraft tailhook.

[0007] Furthermore, the locking hook units on the arresting cable are multiple and evenly arranged.

[0008] Furthermore, the connecting structure includes a rolling bearing, the inner wall of which is fixedly sleeved on the outer wall of the barrier cable, and the outer wall of the rolling bearing is fixedly connected to the elastic locking structure.

[0009] Furthermore, the outer wall of the rolling bearing and the elastic locking structure are rigidly connected by a bolt structure.

[0010] Furthermore, the elastic locking structure includes an elastic metal sheet, which is in a strip shape arranged along the extension direction of the arresting cable under natural conditions. When the aircraft tailhook contacts the elastic metal sheet, the elastic metal sheet undergoes elastic deformation and wraps around the arresting cable.

[0011] Furthermore, the elastic metal sheet is made of high-elasticity steel.

[0012] Furthermore, the cross-sectional profile of the elastic metal sheet is arched, and the direction of the arched protrusion is away from the blocking cable.

[0013] Furthermore, the cross-sectional profile of the elastic metal sheet is an arc shape that conforms to the outer wall of the arresting cable.

[0014] The beneficial effects of this utility model are:

[0015] By setting up a locking hook unit, the decoupling rate of the aircraft's tailhook and arresting cable can be reduced, thereby improving the problems such as increased risk of landing failure and threats to flight safety caused by tailhook decoupling from the arresting cable. Attached Figure Description

[0016] Figure 1 This is a three-dimensional schematic diagram of the present invention in its natural state;

[0017] Figure 2 This is a schematic diagram of the elastic deformation state of the elastic metal sheet of this utility model;

[0018] Figure 3 This is a cross-sectional schematic diagram of the present invention;

[0019] The diagram is labeled as follows: 1-barrier cable, 2-elastic metal sheet, 3-connecting structure, 31-rolling bearing, 32-bolt structure. Detailed Implementation

[0020] The present invention will be further described below with reference to the accompanying drawings.

[0021] according to Figures 1-3 As shown in the figure, this application proposes an automatic locking hook device for aircraft arresting cables, including an arresting cable 1. The arresting cable 1 is provided with a locking hook unit. The locking hook unit includes an elastic locking structure and a connecting structure 3. The connecting structure 3 is used to connect the elastic locking structure and the arresting cable 1. The elastic locking structure is used to lock the aircraft tailhook and the arresting cable 1 when subjected to the force of the aircraft tailhook. The locking hook unit is set at a preset hook-attacking position on the arresting cable 1 to ensure that the locking hook unit can stably form a locking hook effect.

[0022] Specifically, during the landing process of the aircraft in different attitudes, the tailhook may contact different positions of the arresting cable 1. In order to ensure that the tailhook can trigger the locking hook unit, there are multiple locking hook units evenly arranged on the arresting cable 1. The specific distribution of the positions can be designed by range based on the contact points between the tailhook and the arresting cable 1 in multiple flight landing experiments. This ensures that locking hook units are arranged at all points on the arresting cable 1 that may be hit by the tailhook, so that the tailhook can accurately contact the locking hook unit and achieve a locking effect when the aircraft lands.

[0023] Under normal circumstances, it is difficult to ensure that the tailhook is exactly in the center of the arresting cable 1 during aircraft landing. During the dragging of the arresting cable 1, sliding friction will occur between the tailhook and the arresting cable 1, causing significant wear and tear and reducing the service life of the arresting cable 1. In order to improve the above problems, the connection structure includes a rolling bearing 31. The inner wall of the rolling bearing 31 is fixedly sleeved on the outer wall of the arresting cable 1, and the outer wall of the rolling bearing 31 is fixedly connected to the elastic locking structure. The relative displacement is achieved by the rolling friction between the rolling bearing 31 and the arresting cable 1, which greatly reduces the friction loss of the arresting cable 1, reduces the raw material cost and equipment maintenance time cost of the arresting cable 1, and at the same time avoids the arresting cable 1 from breaking, further ensuring safety. Moreover, the outer wall of the outer sleeve of the rolling bearing 31 and the elastic locking structure are rigidly connected by a bolt structure 32. The bolt structure 32 is an existing high-strength bolt structure 32, which ensures that the elastic locking structure will not fall off under the high-intensity impact of the aircraft tailhook.

[0024] Regarding the aforementioned elastic locking structure, one embodiment of this invention can be a spring-loaded snap-fit ​​clamping structure. The snap-fit ​​clamping structure is in an open state under natural conditions, and a spring is installed between the two clamping parts of the snap-fit ​​clamping structure. The snap-fit ​​structure achieves a snap-fit ​​effect, allowing the snap-fit ​​clamping structure to be in an unfolded state, while the spring is compressed. A corresponding triggering structure is installed at the position where the arresting cable 1 impacts the aircraft tailhook. The triggering structure is connected to the snap-fit ​​structure. When the aircraft tailhook touches the triggering structure of the arresting cable 1, the two clamping parts of the snap-fit ​​clamping structure quickly approach each other under the spring force, achieving a locking effect on the aircraft tailhook.

[0025] To reduce costs and simplify the structure, the elastic locking structure in this embodiment can be an elastic metal sheet 2 in another implementation. The elastic metal sheet 2 is naturally strip-shaped and extends along the direction of the arresting cable 1, and its size can cover a certain length, ensuring that the aircraft tailhook is stably locked. When the aircraft tailhook contacts the elastic metal sheet 2, the elastic metal sheet 2 undergoes elastic deformation and wraps around the arresting cable 1. Since the main resistance and hooking effect when the aircraft lands and acts on the arresting cable 1 are based on the interaction force between the aircraft tailhook and the arresting cable 1, the elastic metal sheet 2 in this embodiment plays an auxiliary role in force by wrapping around the outer wall of the aircraft tailhook, which can improve the connection stability between the aircraft tailhook and the arresting cable 1 and reduce the decoupling rate to a certain extent.

[0026] Specifically, the elastic metal sheet 2 is made of high-elasticity steel, which has excellent corrosion resistance and impact resistance. In the highly corrosive environment of an aircraft carrier, high-elasticity steel not only maintains stable performance over a long period of time, but also exhibits high strength and toughness when subjected to extreme impacts such as the tailhook strike. Furthermore, its long service life and good fatigue resistance meet the requirement of repeated use of the arresting cable 1. In material parameter simulation experiments, the elastic modulus of high-elasticity steel is approximately 200 GPa, and its yield strength is approximately 350 MPa. During the aircraft's landing and taxiing to a stop, the main kinetic energy of the tailhook is transmitted through the arresting cable 1. The elastic steel sheet mainly plays an auxiliary role in the stress, i.e., undergoing elastic deformation to provide fixation. It only needs to ensure that its shape does not change significantly during deformation. The required elastic modulus is approximately 50 GPa, and the yield strength is approximately 120 MPa. Therefore, these material parameters meet the requirements and have a large load-bearing margin. The elastic metal sheet 2 can also be made of existing elastic shape memory alloy materials.

[0027] In addition, in order to ensure that the elastic metal sheet 2 can react quickly and deform elastically after being impacted by the aircraft tailhook in its naturally extended state, in one embodiment, the cross-sectional profile of the elastic metal sheet 2 is arched, and the direction of the arch protrusion is away from the arresting cable 1. This arched design can play a stable supporting role in the naturally extended state. When impacted and deformed, a large amount of elastic stress is released, and the supporting role of the arch quickly fails, so that the elastic metal sheet 2 can deform quickly and tightly wrap around the outside of the aircraft tailhook. In another embodiment, the cross-sectional profile of the elastic metal sheet 2 is an arc shape that conforms to the outer wall of the arresting cable 1. The principle is similar to that of the arch, but it adapts to the characteristics of the outer wall of the arresting cable 1, making the structure of the elastic metal sheet 2 more stable in its natural state.

[0028] The actual working principle of the automatic locking device for aircraft arresting cables is as follows: When the aircraft lands, the inner wall of the aircraft tailhook impacts the position of the elastic metal plate 2. The elastic metal plate 2 quickly undergoes elastic deformation and wraps around the outer wall of the aircraft tailhook. At this time, the aircraft tailhook is locked by the elastic metal plate 2, reducing the unhooking rate. However, the actual arresting force is borne by the arresting cable 1 itself. During the process of the aircraft tailhook pulling the arresting cable 1 to move, the aircraft tailhook rotates relative to the arresting cable 1. At this time, under the action of the rolling bearing 31, the sliding friction force is converted into the rolling friction force of the roller, reducing wear.

[0029] In summary, this application provides an automatic locking device for aircraft arresting cables. When the elastic metal sheet 2 collides with the aircraft tailhook, it will trigger its elastic deformation to tightly wrap around the aircraft tailhook, effectively preventing it from detaching. The elastic metal sheet 2 is connected to the arresting cable 1 through a bearing, which changes the original sliding friction between the aircraft tailhook and the arresting cable 1 to rolling friction, effectively reducing friction loss and significantly improving the service life of the arresting cable 1.

Claims

1. An automatic locking hook device for aircraft arresting cables, comprising an arresting cable (1), characterized in that, The arresting cable (1) is provided with a locking hook unit, which includes an elastic locking structure and a connecting structure (3). The connecting structure (3) is used to connect the elastic locking structure and the arresting cable (1). The elastic locking structure is used to lock the aircraft tailhook and the arresting cable (1) when subjected to the force of the aircraft tailhook.

2. The automatic locking hook device for aircraft arresting cables according to claim 1, characterized in that, The locking hook units on the arresting cable (1) are multiple units that are evenly arranged.

3. The automatic locking hook device for aircraft arresting cables according to claim 1, characterized in that, The connection structure includes a rolling bearing (31), the inner wall of which is fixedly sleeved on the outer wall of the barrier cable (1), and the outer wall of which is fixedly connected to the elastic locking structure.

4. The automatic locking hook device for aircraft arresting cables according to claim 3, characterized in that, The outer wall of the rolling bearing (31) and the elastic locking structure are rigidly connected by a bolt structure (32).

5. The automatic locking hook device for aircraft arresting cables according to claim 3, characterized in that, The elastic locking structure includes an elastic metal sheet (2). Under natural conditions, the elastic metal sheet (2) is in a strip shape along the extension direction of the arresting cable (1). When the aircraft tailhook contacts the elastic metal sheet (2), the elastic metal sheet (2) undergoes elastic deformation and wraps around the arresting cable (1).

6. The automatic locking hook device for aircraft arresting cables according to claim 5, characterized in that, The elastic metal sheet (2) is made of high-elastic steel.

7. The automatic locking hook device for aircraft arresting cables according to claim 6, characterized in that, The cross-sectional profile of the elastic metal sheet (2) is arched, and the direction of the arched protrusion is away from the blocking cable (1).

8. The automatic locking hook device for aircraft arresting cables according to claim 6, characterized in that, The cross-sectional profile of the elastic metal sheet (2) is an arc shape that conforms to the outer wall of the barrier cable (1).

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